JP2902071B2 - Helicopter rotor vibration isolator - Google Patents
Helicopter rotor vibration isolatorInfo
- Publication number
- JP2902071B2 JP2902071B2 JP2203909A JP20390990A JP2902071B2 JP 2902071 B2 JP2902071 B2 JP 2902071B2 JP 2203909 A JP2203909 A JP 2203909A JP 20390990 A JP20390990 A JP 20390990A JP 2902071 B2 JP2902071 B2 JP 2902071B2
- Authority
- JP
- Japan
- Prior art keywords
- rotor blade
- tracking
- control rod
- pitch control
- rotor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/008—Rotors tracking or balancing devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
- B64C2027/004—Vibration damping devices using actuators, e.g. active systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/72—Means acting on blades
- B64C2027/7205—Means acting on blades on each blade individually, e.g. individual blade control [IBC]
- B64C2027/7211—Means acting on blades on each blade individually, e.g. individual blade control [IBC] without flaps
- B64C2027/7216—Means acting on blades on each blade individually, e.g. individual blade control [IBC] without flaps using one actuator per blade
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/30—Wing lift efficiency
Description
【発明の詳細な説明】 〔産業上の利用分野〕 本発明はヘリコプタロータブレードのトラッキング
（回転軌跡）自動調整によりロータ（ブレード）の防振
を行なう防振装置に関する。Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an anti-vibration device for performing vibration control of a rotor (blade) by automatically adjusting tracking (rotation trajectory) of a helicopter rotor blade.
第５図は従来のヘリコプタのロータブレードのトラッ
キング調整装置の一つを取出して示した側面図でロータ
ブレード12のトラッキング調整は、ロータブレード12を
回転させて翼端のトラッキングを計測し、基準に入らな
いロータブレード12があれば、地上でロータブレード12
の回転を停止の上、ピッチコントロールロッド11の長さ
をシム調整により調整し、再度ロータブレード12を回転
させるという作業を繰り返すことでトラッキングが適正
な状態におさまるようにしていた。FIG. 5 is a side view showing one of the conventional helicopter rotor blade tracking adjustment devices. The tracking adjustment of the rotor blade 12 is performed by rotating the rotor blade 12 and measuring the tracking of the wing tip, based on the reference. If there is a rotor blade 12 that does not enter,
After stopping the rotation, the length of the pitch control rod 11 is adjusted by shim adjustment, and the operation of rotating the rotor blade 12 again is repeated so that the tracking can be properly controlled.
〔発明が解決しようとする課題〕 上記従来のヘリコプタロータブレードのトラッキング
調整装置には解決すべき次の課題があった。[Problem to be Solved by the Invention] The conventional helicopter rotor blade tracking adjustment device has the following problems to be solved.
即ち、従来のトラッキング調整ではトラッキング測
量、着陸ロータ停止、シム調整等すべて人間の手で行っ
ていたため、時間がかかり又調整に熟練を要するという
問題があった。又飛行中にガタが発生し調整が狂った場
合には、これを飛行中に再調整することは不可能であ
り、振動の多い状態で飛行することを余儀なくされた。
上記問題点に鑑み、本発明は飛行状態のまま、トラッキ
ングを測り、アンバランスなロータブレードがあれば自
動的にそのロータブレードのロッド長を調整してトラッ
キングを基準内におさめ振動を減衰させることのできる
ヘリコプタロータ防振装置の提供を目的とする。That is, in the conventional tracking adjustment, since tracking survey, landing rotor stop, shim adjustment, and the like are all performed manually, there is a problem that it takes time and requires skill in the adjustment. If the backlash is generated during the flight and the adjustment is out of order, it is impossible to readjust it during the flight, and the flight must be performed in a state of high vibration.
In view of the above problems, the present invention measures tracking while flying, and automatically adjusts the rod length of the rotor blade if there is an unbalanced rotor blade to keep tracking within the reference to attenuate vibration. It is an object of the present invention to provide a helicopter rotor anti-vibration device.
本発明は上記課題を解決手段として、ロータブレード
の付根部に設けられたピッチコントロールロッドの長さ
を調整してロータブレードのトラッキングを基準内に維
持し、ロータブレードの防振を行なうヘリコプタロータ
防振装置において、軸方向の中央近傍で軸に垂直に２分
割されると共に双方の該分割端側に相互に左右逆ネジを
施されたピッチコントロールロッドと、前記ピッチコン
トロールロッドの双方の分割端に螺合すると共に外周に
噛合歯を有するギヤ状の接続子と、前記接続子の外周と
噛合うと共にモータによって往復回転されるギヤと、前
記トラッキングを検出して前記ロータブレードをトラッ
キング基準内に維持する修正信号を前記モータに出力す
る制御器とを具備してなることを特徴とするヘリコプタ
ロータ防振装置を提供しようとするものである。SUMMARY OF THE INVENTION The present invention provides a helicopter rotor protection device that adjusts the length of a pitch control rod provided at the base of a rotor blade to maintain the tracking of the rotor blade within a standard and performs vibration isolation of the rotor blade. In the vibration device, a pitch control rod divided into two parts perpendicular to the axis near the center in the axial direction and having left and right reverse screws on both of the divided ends, and two divided ends of the pitch control rod. A gear-shaped connector that is screwed and has meshing teeth on the outer periphery, a gear that meshes with the outer periphery of the connector and is reciprocally rotated by a motor, detects the tracking, and maintains the rotor blade within a tracking reference. A controller for outputting a correction signal to the motor. It is intended to.
本発明は上記のように構成されるので次の作用を有す
る。The present invention has the following effects because it is configured as described above.
即ち、ヘリコプタの各ロータブレードの付根部に取り
付けられたピッチコントロールロッドを軸に垂直に２分
割し、各分割端に相互に左右逆ネジを施して、これら双
方をギヤ状の接続子に螺合、モータ付きのギヤに噛合わ
せて往復回転させるので、モータに回転指令を与えるだ
けで、ピッチコントロールロッドの綜合長さを伸縮させ
ることができ、飛行中でもトラッキング調整ができる。That is, the pitch control rod attached to the root of each rotor blade of the helicopter is divided into two parts perpendicular to the axis, and left and right reverse screws are applied to each of the divided ends, and these are screwed into gear-like connectors. Since the gears are reciprocally rotated by gearing with a motor-equipped gear, the total length of the pitch control rod can be expanded and contracted only by giving a rotation command to the motor, and tracking adjustment can be performed even during flight.
本発明の一実施例を第１図〜第４図により説明する。 One embodiment of the present invention will be described with reference to FIGS.
第１図は本実施例のヘリコプタロータ防振装置を備え
たヘリコプタの俯瞰図、第２図は第１図の囲いIIの部位
の拡大側断面図、第３図は第２図のIII−III矢視断面
図、第４図は本実施例によるトラッキング調整のシステ
ムブロック図である。1 is an overhead view of a helicopter provided with the helicopter rotor anti-vibration device of the present embodiment, FIG. 2 is an enlarged sectional side view of a portion of an enclosure II in FIG. 1, and FIG. 3 is III-III in FIG. FIG. 4 is a system block diagram of tracking adjustment according to the present embodiment.
第１図〜第３図においてロータブレード12の付根部に
は各ロータブレード12毎に上部ピッチコントロールロッ
ド１がピン結合され、それらに対応して下方には下部ピ
ッチコントロールロッド４が回転シザー６にピン結合さ
れており、上部ピッチコントロールロッド１の下部及び
下部ピッチコントロールロッド４の上部にはそれぞれ相
互に逆向き、即ち左ネジ及び右ネジが施されて接続子２
のネジ穴に相互が上下に一直線状に螺入されている。即
ち、たとえば接続子２の右回転では第２図の点a,b間は
伸び、左回転では短縮するよう（或はそれらの逆に）構
成されている。接続子２はギヤ状をなしており、外周に
施された歯にはギヤ３が噛み合い、ギヤ３はモータ５の
軸に固設され、モータ５が回転すれば、その回転の向き
に応じて上記点a,b間が伸縮してロータブレード12のピ
ッチがコントロールされる。1 to 3, an upper pitch control rod 1 is pin-connected to the root of the rotor blade 12 for each rotor blade 12, and a lower pitch control rod 4 is attached to the rotating scissor 6 correspondingly below. Pins are connected, and the lower part of the upper pitch control rod 1 and the upper part of the lower pitch control rod 4 are oppositely oriented to each other, that is, left-handed and right-handed.
Are screwed up and down in a straight line. That is, for example, when the connector 2 is rotated clockwise, it extends between points a and b in FIG. 2, and when it is rotated counterclockwise, it contracts (or vice versa). The connector 2 has a gear shape, and a gear 3 meshes with teeth provided on the outer periphery, and the gear 3 is fixed to a shaft of the motor 5, and when the motor 5 rotates, the gear 3 according to the rotation direction. The pitch between the rotor blades 12 is controlled by the expansion and contraction between the points a and b.
モータ５には、第４図のシステムブロック図に示すよ
うにロータブレード12翼端のトラッキング状態を示す信
号、たとえばロータブレード12の翼端に設けた反射板の
ストロボライトへの反射信号が増巾器７及び制御器８を
介してその回転方向及び回転角を指示する信号として伝
わり、その指示に沿って複数のうちの所定のモータ５が
所要量回転することにより、上記点a,b間の距離、即
ち、上部ピッチコントロールロッド１、接続子２、下部
ピッチコントロールロッド４の綜合長さが調整される。
これによってロータブレード12の翼端のトラッキングを
基準値内におさめることができ、ロータブレード12のト
ラッキングに基因する振動が減衰する。As shown in the system block diagram of FIG. 4, a signal indicating the tracking state of the rotor blade 12 blade tip, for example, a reflection signal to a strobe light of a reflector provided on the rotor blade 12 blade tip is amplified by the motor 5. The signal is transmitted as a signal indicating the rotation direction and the rotation angle through the device 7 and the controller 8, and a predetermined amount of the plurality of motors 5 is rotated by a required amount according to the instruction. The distance, that is, the total length of the upper pitch control rod 1, the connector 2, and the lower pitch control rod 4 is adjusted.
Thereby, the tracking of the blade tip of the rotor blade 12 can be kept within the reference value, and the vibration caused by the tracking of the rotor blade 12 is attenuated.
以上の調整は飛行時、ホバリング時、着地時を問わ
ず、ロータ回転中は自動的かつ迅速に行なうことができ
る。The above adjustment can be performed automatically and quickly during rotation of the rotor, regardless of flight, hovering, or landing.
以上の通り、本実施例によればヘリコプタのロータブ
レードのトラッキング調整を飛行中、着地中を問わず随
時、かつ迅速に行なうことができるので常に振動のない
円滑なフライトが行なえるという利点がある。また、ト
ラッキング調整を格別の作業員を要することなく行な
え、熟練者を必要としないという利点もある。As described above, according to the present embodiment, the tracking adjustment of the rotor blade of the helicopter can be performed at any time and during the flight, regardless of whether it is in flight or while landing. . In addition, there is an advantage that the tracking adjustment can be performed without requiring a special worker, and no skilled person is required.
本発明は上記のように構成されるので次の効果を有す
る。The present invention has the following effects because it is configured as described above.
即ち、飛行状態のままでもロータブレードのトラッキ
ングの修正が可能で振動のないヘリコプタが得られる。That is, it is possible to obtain a helicopter in which the tracking of the rotor blade can be corrected even in the flying state and vibration free.
第１図は本発明の一実施例に係るヘリコプタロータ防振
装置を備えたヘリコプタの俯瞰図、第２図は第１図の囲
いIIの部位の拡大側面図、第３図は第２図のIII−III矢
視断面図、第４図は上記実施例によるトラッキング調整
のシステムブロック図、第５図は従来のロータブレード
のトラッキング調整装置の側面図である。 １……上部ピッチコントロールロッド， ２……接続子,3……ギヤ， ４……下部ピッチコントロールロッド， ５……モータ,6……回転シザー， ７……増幅器（A/D変換）， ８……制御器（計算器）， 12……ロータブレード。FIG. 1 is a bird's-eye view of a helicopter provided with a helicopter rotor vibration isolator according to one embodiment of the present invention, FIG. 2 is an enlarged side view of a portion of enclosure II in FIG. 1, and FIG. FIG. 4 is a system block diagram of tracking adjustment according to the above embodiment, and FIG. 5 is a side view of a conventional rotor blade tracking adjustment device. 1 ... upper pitch control rod, 2 ... connector, 3 ... gear, 4 ... lower pitch control rod, 5 ... motor, 6 ... rotating scissor, 7 ... amplifier (A / D conversion), 8 …… Controller (calculator), 12 …… Rotor blade.
Claims (1)
チコントロールロッドの長さを調整してロータブレード
のトラッキングを基準内に維持し、ロータブレードの防
振を行なうヘリコプタロータ防振装置において、軸方向
の中央近傍で軸に垂直に２分割されると共に、双方の該
分割端側に相互に左右逆ネジを施されたピッチコントロ
ールロッドと、前記ピッチコントロールロッドの双方の
分割端に螺合すると共に、外周に噛合歯を有するギヤ状
の接続子と、前記接続子の外周と噛合うと共にモータに
よって往復回転されるギヤと、前記トラッキングを検出
して前記ロータブレードをトラッキング基準内に維持す
る修正信号を前記モータに出力する制御器とを具備して
なることを特徴とするヘリコプタロータ防振装置。A helicopter rotor vibration isolator for adjusting the length of a pitch control rod provided at the root of a rotor blade to maintain tracking of the rotor blade within a reference and perform vibration isolation of the rotor blade. A pitch control rod which is vertically divided into two parts in the vicinity of the center in the direction and is provided with right and left reverse screws on both of the divided ends, and is screwed into both divided ends of the pitch control rod. A gear-shaped connector having meshing teeth on the outer periphery, a gear meshing with the outer periphery of the connector and reciprocatingly rotated by a motor, and a correction signal for detecting the tracking and maintaining the rotor blade within a tracking reference. A helicopter rotor vibration isolator comprising:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2203909A JP2902071B2 (en) | 1990-08-02 | 1990-08-02 | Helicopter rotor vibration isolator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2203909A JP2902071B2 (en) | 1990-08-02 | 1990-08-02 | Helicopter rotor vibration isolator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0490999A JPH0490999A (en) | 1992-03-24 |
| JP2902071B2 true JP2902071B2 (en) | 1999-06-07 |
Family
ID=16481708
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2203909A Expired - Lifetime JP2902071B2 (en) | 1990-08-02 | 1990-08-02 | Helicopter rotor vibration isolator |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2902071B2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4615482B2 (en) * | 2006-06-09 | 2011-01-19 | 川崎重工業株式会社 | Vibration reduction method, vibration reduction support device, and program |
| CN104675635B (en) * | 2015-03-10 | 2018-02-13 | 哈尔滨工程大学 | A kind of oscillating airfoil TRT equipped with corner amplifier |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3786695A (en) * | 1972-04-28 | 1974-01-22 | Boeing Co | Redundant pitch link |
| US4304375A (en) * | 1979-05-17 | 1981-12-08 | Textron Inc. | Electrically controlled elevator |
-
1990
- 1990-08-02 JP JP2203909A patent/JP2902071B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0490999A (en) | 1992-03-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR910004005B1 (en) | Motion responsive wind turbine tower damping | |
| US4105363A (en) | Overspeed control arrangement for vertical axis wind turbines | |
| KR101217804B1 (en) | Bottom propeller control type vehicle | |
| JP2019163050A5 (en) | ||
| JP3051357B2 (en) | Main rotor torque correction device | |
| US5409183A (en) | Helicopter with leading edge servo flaps for pitch positioning its rotor blades | |
| CA2906500C (en) | Rotor assembly apparatus | |
| BRPI0620943A2 (en) | airfoil for an aircraft and aircraft | |
| CN109878715B (en) | Fault monitoring and early warning method for unmanned aerial vehicle and unmanned aerial vehicle | |
| KR101217803B1 (en) | Bottom three-propeller control type vehicle | |
| JP2009541143A (en) | Adjusting device for adjusting pitch angle of propeller blade, variable pitch propeller, control function executable in computer, and method for adjusting pitch angle of propeller blade | |
| JP2902071B2 (en) | Helicopter rotor vibration isolator | |
| CN111591462A (en) | Helicopter tail rotor simulation system for wind tunnel test | |
| JPH03933A (en) | Method and device for controlling aircraft propeller speed and ground mode of pitch | |
| CN106828903B (en) | Supporting structure and unmanned aerial vehicle | |
| US4474531A (en) | Windmill with direction-controlled feathering | |
| US9527579B2 (en) | Pivoting blade counterweight | |
| Mort et al. | Aerodynamic characteristics of a 4-foot-diameter ducted fan mounted on the tip of a semispan wing | |
| US20160186584A1 (en) | Turbomachine impellor rotor with device for feathering the blades of the impellor | |
| US3176774A (en) | Helicopter drive control | |
| CN209237190U (en) | A kind of novel radiotherapy collimator and radiotherapy unit | |
| Yaggy et al. | Aerodynamics of a tilting ducted fan configuration | |
| JP2001099045A (en) | Blade pitch variable mechanism for wind mill | |
| US4518313A (en) | Wind blade vibration eliminator for helicopters | |
| EP4086032A1 (en) | Multi-link linkage angle accessory head |